Experimental Study of Vortex Shedding Control Using Plasma Actuator

This paper aims at experimental investigation of the active flow control with plasma actuator over an airfoil. The method involved application of single dielectric barrier discharge in order to change the frequency of vortex shedding and the turbulence characteristics from a NACA4412 airfoil. The objective was to reduce control flaps noise in transporting aircraft via an effective body force generated by the actuators. Results indicated that the use of plasma actuator led to a significant decrease in the frequency of vortex shedding around the flap whereas a significant increase in turbulence levels was achieved at a distance away from the actuator.